CN105781920A - Magnetic plasma thrustor supported through lasers - Google Patents
Magnetic plasma thrustor supported through lasers Download PDFInfo
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- CN105781920A CN105781920A CN201610273464.9A CN201610273464A CN105781920A CN 105781920 A CN105781920 A CN 105781920A CN 201610273464 A CN201610273464 A CN 201610273464A CN 105781920 A CN105781920 A CN 105781920A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
Abstract
The invention provides a magnetic plasma thrustor supported through lasers. The magnetic plasma comprises a thrustor power source for supplying power to all electric equipment in the thrustor; satellite platform electric energy is converted through the thrustor power source to be then supplied to the thrustor; the magnetic plasma thrustor further comprises a working medium supply device, a negative pole, a positive pole and a laser generation mechanism, a discharge channel is formed between the negative pole and the positive pole, the working medium feeding device used for fixing and conveying a working medium is arranged outside the discharge channel, and the working medium is a solid working medium and extends into the discharge channel; and the laser generation mechanism emits laser beams into the discharge channel to conduct ablation on the working medium, the laser beams conduct ablation on the working medium continuously to generate partial ionized gas and particulate matter, and the partial ionized gas and the particulate matter enter the discharge channel. The magnetic plasma thrustor solves the problems that an air supply system is complex, dynamic response is slow, negative pole ablation is serious, and performance reduction is caused by large-current vibration, and the magnetic plasma thrustor which is supported through the lasers and is high in dynamic response, high in working medium using rate and high in energy conversion efficiency is provided for a spacecraft.
Description
Technical field
The present invention relates to a kind of for spacecraft orbit lifting, survey of deep space, the manned electric propulsion system logging in the space tasks such as Mars.Especially one utilizes laser gasification partial ionization solid working medium, mainly with electromagnetic force acceleration, with the magnetic plasma propeller of quasi-steady state or steady operation.
Background technology
Magnetic plasma propeller (Magnetoplasmadynamicthruster, MPDT) it is the electric propulsion system of a kind of electromagnetism accelerating type, there is ratio leap high (1000～10000s), efficiency high (higher than 30%), thrust big (can more than 10N), the advantages such as pushing force density is big and mass of system is little, become the thruster being best suitable for docking with high-power space solar and nuclear power system, in Large Spacecraft lifting track, interplanetary navigation and survey of deep space etc., there is significant advantage.
Magnetic plasma propeller generally comprises the parts such as power supply, working substance supply system, electromagnetism accelerator (i.e. thruster body), and complementary field (for complementary field MPDT, AF-MPDT, Applied-FieldMPDT).Thruster body includes the parts such as central cathode, cylindrical anode and working medium supply line, valve, anode and negative electrode coaxially and surround negative electrode, and during thruster work, gas working medium injects from thruster head, forming high current arc between anode and cathode, electric arc ionizes and accelerates working medium.Working medium is generally hydrogen, argon or lithium vapor.Different according to thruster mode of operation, quasi-steady state MPDT and stable state MPDT can be divided into；Produce principle according to magnetic field different, self-induction magnetic field MPDT (Self-FieldMPDT, SF-MPDT) and complementary field MPDT (AF-MPDT) can be divided into.
MPDT has irreplaceable advantage in interplanetary navigation and survey of deep space etc., but understanding and the grasp of MPDT working mechanism are also nowhere near by people.Although MPDT has been carried out exploration for many years and research by domestic and international researcher, but MPDT thrust is constituted and electromagnetic coupled acceleration mechanism is still without understanding fully completely, completely can not accurately describe the detailed operation of MPDT.Still do not carry out the MPTD of space flight test at present, main reason is that MPDT there is problems in that
(1) air supply system is complicated, and dynamic response is slow.MPDT needs complicated working medium storage device and complicated air supply system to provide gaseous working medium for thruster, by the restriction of air supply system pipeline and valve, MPDT works low-response, and when thruster is with quasi-steady operation, supply and electric discharge are difficult to synchronize, and cause the waste of working medium.
(2) cathode burning corrosion is serious.Owing to MPDT power is high, in work process, discharge current is big, and cathode temperature is high, easily causes the serious ablation of negative electrode, thus reducing the working life of thruster.Although having adopted at present the thruster configuration of hollow cathode, reduce the temperature of negative electrode in thruster work process, but the problem still suffering from cathode burning corrosion.
(3) big current oscillation phenomenon (" onset " phenomenon).Under big electric current (> 5000A) duty, there is unstable oscillation in thruster discharge current and voltage, and thruster energy conversion efficiency declines, and has a strong impact on performance and the life-span of thruster.
Summary of the invention
For magnetic plasma propeller air supply system complexity, dynamic response is slow, cathode burning corrosion is serious and big current oscillation causes the problems such as performance reduction, it is an object of the invention to provide a kind of dynamic response magnetic plasma propeller that laser fast, working medium utilization rate height, energy conversion efficiency height, simple in construction, reliability height, long service life is supported for spacecraft.
The technical scheme is that
The magnetic plasma propeller that a kind of laser is supported, including the thruster power supply powered to electrical equipment each in thruster, thruster power supply is supplied to thruster after converted for satellite platform electric energy, this thruster also includes working substance supply device, negative electrode, anode, laser generating mechanism, discharge channel is defined between negative electrode and anode, it is arranged on outside discharge channel for fixing and transferring working medium working substance supply device, described working medium is solid working medium, working medium stretches in discharge channel, laser instrument generating mechanism launches laser beam ablation working medium in discharge channel, laser beam continuous ablation working medium generating section ionized gas and particulate matter enter among discharge channel.
Further, the thruster of the present invention also includes controller, described controller is connected with thruster power supply and laser generating mechanism, the electric current of monitoring control devices thruster power supply output and voltage, control the laser power of laser generating mechanism output, regulate its output beam quality, spot size and focal position, thus quickly regulating the ablation velocity of working medium and plasma parameter to reach to control the effect of interelectrode voltage and current.
Further, laser generating mechanism of the present invention includes beam control system and laser instrument, described beam control system and laser instrument are all connected with controller, the laser power of laser instrument output is by controller control, and the laser beam of laser instrument output is regulated output beam quality, spot size and focal position by beam control system.
Further, laser generating mechanism of the present invention also includes plume preventer, and described plume protection dress is being positioned on the laser optical path between beam control system and discharge channel, for preventing the optical mirror plane of plume contamination beam control system.
Heretofore described negative electrode is solid or hollow cylinder structure, and described anode is nozzle type or the cylinder cartridge type of the shrinkage expansion of boring, and described negative electrode is arranged on anode interior and negative electrode and anode is coaxially disposed.Now, described working medium can simultaneously as negative electrode, and working medium is arranged on anode interior and working medium as negative electrode and anode is coaxially disposed.
Further, when above-mentioned negative electrode and anode are coaxially disposed, described laser beam can export directive working medium from discharge channel, the central axis of laser beam and coaxial type anode forms an angle, the angle of angle ensure laser beam can ablation working medium when big as far as possible, plume preventer deviates the central shaft of coaxial type anode as far as possible in thruster physical dimension allowed band simultaneously.Or, described anode offers the through hole for laser beam traverse, the through hole directive working medium that described laser beam is offered on anode.
Further, when above-mentioned negative electrode and anode are coaxially disposed, if self-induction magnetic field intensity is inadequate, field coil can be installed additional outside thruster anode, field coil is powered by field coil power supply, field coil produces approximately along the axial complementary field of thruster to improve thruster performance, simultaneously, it is possible to be designed accelerating better plasma to field coil and externally-applied magnetic field.Further, controller can control field coil power supply, regulates the size of current of field coil, thus strengthening or reducing externally-applied magnetic field.
Described negative electrode and anode in the present invention also can adopt slab construction, and described negative electrode is parallel with anode or arranges in certain subtended angle.
When negative electrode and anode adopt slab construction, negative electrode is parallel with anode or arranges in certain subtended angle, forms discharge channel between negative electrode and anode.In this case, laser beam can from the side directive working medium of discharge channel.The through hole for laser beam traverse can also be offered, the through hole directive working medium that described laser beam is offered on yin, yang pole plate on described yin, yang pole plate.It is possible to further arrange permanent magnet or solenoid in discharge channel both sides, produce with self induction magnetic field complementary field in the same direction to promote thruster propulsive performance.
Laser instrument in the present invention can work or Burst-mode operation in a continuous mode, and when working in a pulsed mode, pulse frequency is sufficiently high, to keep the approximate continuity of working medium ablation.
The Advantageous Effects of the present invention:
The magnetic plasma propeller of laser support utilizes laser ablation solid working medium to produce high-rate laser plasma flow, and air-flow obtains dissociation, ionization further in thruster discharge channel and accelerates, so that working medium obtains higher ionization rate and injection rate.Laser technology is applied to MPDT and is possible not only to overcome the inherent defect of MPDT, promotes its performance, and can for disclosing MPDT work process and electromagnetism acceleration mechanism provides new ways and means.The advantage of laser ablation MPDT is embodied in following several respects:
(1) thruster adopts solid working medium.Do not need air supply system, while reducing thruster quality and volume, be greatly improved the work response time of thruster.
(2) working medium is required low, ablation amount controllable precise.Various material can be adopted as working medium, and metal, polymer and the mixture of the two can serve as working medium, and working medium ablation amount can be passed through to regulate laser parameter and accurately control, and this is the tradition MPDT advantage not possessed.
(3) coaxial type laser ablation MPDT, the negative electrode of thruster can simultaneously as working medium.Using thruster negative electrode as working medium, it is possible to resolve thruster cathode burning corrosion problem, be conducive to improving thruster working life.
(4) thruster working medium utilization rate is high, system effectiveness is high, ratio is leapt high.In the laser ablation stage, the partial ionization of ablated working medium, and laser ablation produce working medium there is higher initial velocity.At follow-up electromagnetism boost phase, air-flow is ionized further and is accelerated so that ionization rate and the utilization rate of working medium are greatly improved, thus the working medium utilization rate of thruster, system effectiveness are compared tradition MPDT and can be significantly improved with specific impulse.
In sum, laser ablation MPDT has working medium ablation amount controllable precise, working medium utilization rate is high, thrust response is fast, than leaping high, system effectiveness advantages of higher, can promote for spacecraft orbit, survey of deep space, the manned space tasks such as Mars that log in provide the propulsion system of a kind of efficient advanced persons.
Accompanying drawing explanation
Fig. 1 is the structural representation of one specific embodiment of magnetic plasma propeller that laser of the present invention is supported；
Fig. 2 is that coaxial type thruster working medium is as negative electrode schematic diagram；
Fig. 3 is laser traverse coaxial type anode aperture directive working medium schematic diagram；
Fig. 4 is laser from parallel plate electrode side directive working medium schematic diagram；
Fig. 5 is the aperture directive working medium schematic diagram on laser traverse parallel plate electrode.
Fig. 1～5 are denoted as:
1 controller；
2 field coil power supplys；
3 field coils；
4 thruster power supplys；
5 working substance supply devices；
6 working medium；
7 coaxial type negative electrodes；
8 coaxial type anodes；
9 plume preventers；
10 beam control systems；
11 laser instrument；
12 flat board anodes；
13 planar cathodes.
Detailed description of the invention
The present invention provides the magnetic plasma propeller that a kind of laser is supported, it is to utilize laser ablation solid working medium to produce plasma flow, air-flow is ionized further in thruster discharge channel and is accelerated, so that working medium obtains higher ionization rate and injection rate, simultaneously, utilize the capability of fast response of laser, the ablation velocity of working medium, plasma parameter are quickly regulated, to control the voltage and current between thruster sparking electrode, thus eliminating big current oscillation phenomenon and reducing cathode burning corrosion phenomenon.
With reference to Fig. 1, the structural representation of a specific embodiment of the magnetic plasma propeller supported for a kind of laser of the present invention.Including controller 1, thruster power supply 4, working substance supply device 5, working medium 6, coaxial type negative electrode 7, coaxial type anode 8, plume preventer 9, beam control system 10, laser instrument 11 and various support member, connecting line and transmission line, thruster can with steady operation or quasi-steady operation.When thruster power is big, between electrode, electric current is sufficiently large, its self-induction magnetic field is enough to the behavior of about beam ion, now need not set up field coil power supply 2 and field coil 3.When between electrode, electric current is less, its self-induction magnetic field is less, now needs to set up field coil power supply 2 and field coil 3 produces externally-applied magnetic field to retrain the behavior of plasma, to improve thruster performance.Thruster is with stable state and quasi-steady state operation, its work process is: laser instrument 11 is launched light laser ablation working medium 6 end face and formed plasma, induction thruster negative and positive two interpolar forms discharge current, thus forming self induction magnetic field, if electric current is less, field coil 3 produce complementary field, plasma is accelerated ejection by electromagnetic force in thruster discharge channel, thus forming thrust.
Thruster power supply 4, beam control system 10, laser instrument 11 are all connected with controller 1.Controller 1 can pass through to control link external magnetic field coil power 2, thruster power supply 4, beam control system 10 and laser instrument 11 and send control instruction.The Main Function of controller 1 is electric current and the voltage of monitoring thruster power supply 4 output, control beam control system 10 and laser instrument 11, the two is made quickly to adjust laser parameter, thus quickly regulating the ablation velocity of working medium and plasma parameter to reach to control the effect of interelectrode voltage and current.Controller 1 can control the output size of current of external magnetic field coil power 2, thus adjusting the induction level of externally-applied magnetic field.The effect of thruster power supply 4 is to be supplied to thruster after converted for satellite platform electric energy, and controller 1 can send instruction to thruster power supply 4, allows thruster power supply 4 export different power.
With reference to Fig. 1, coaxial type negative electrode 7 is solid cylinder structure, and coaxial type anode 8 is the cylinder cartridge type of boring, and coaxial type negative electrode 7 is arranged on coaxial type anode 8 inside and coaxial type negative electrode 7 and coaxial type anode 8 is coaxially disposed.Discharge channel is defined between coaxial type negative electrode 7 and coaxial type anode 8, it is arranged on outside discharge channel for fixing and transferring working medium 6 working substance supply device 5, described working medium 6 is solid working medium, working medium 6 stretches in discharge channel, laser instrument 11 is launched laser beam ablation working medium, laser beam continuous ablation working medium generating section ionized gas and particulate matter in discharge channel and is entered among discharge channel.
In the present embodiment: laser instrument 11 exports the laser of infrared wavelength, laser power 2000 watts, beam divergence angle is below 0.01 radian, laser beam expands shaping in beam control system 10 and focuses on formation convergent beam, and convergent beam tilts to penetrate the end face of directive working medium 6 through plume preventer 9 and from the discharge channel port of export.The angle of the central axis of laser beam and coaxial type anode is 30 degree, and the distance between plume preventer 9 and working medium 6 end face is longer, to ensure that plume preventer 9 is away from thruster plume center.
In the present embodiment: coaxial type anode 8 material is copper, diameter is 0.2 meter, and coaxial type negative electrode 7 and coaxial type anode 8 are provided stable energy input by thruster power supply 4, and input power is 200 kilowatts.Installing field coil 3 outside described coaxial type anode 8 additional, field coil 3 is powered by field coil power supply 2, and field coil 3 produces along the axial complementary field of thruster to improve thruster performance.Field coil 3 produces stable, to be parallel to discharge channel axis externally-applied magnetic field, and its maximum magnetic induction is 0.1 tesla.The material of working medium 6 is modified Teflon, and laser beam ablation working medium 6 produces plasma jet to putting between coaxial type anode and cathode, and the mass flowrate of working medium ablation is at 0.0001～0.002kg/s.Thruster is with steady operation, and laser ablation working medium forms plasma, and induction thruster two interpolar forms stable discharge current, and discharge current forms self induction magnetic field, plasma discharge electric field and self induction magnetic field and outer in accelerate vertically after to outer ejection.
Controller 1 controlling push-force device power supply 4 output size, thus controlling thrust size.Under the control of controller 1, the laser beam of laser instrument 11 output can be regulated output beam quality, spot size and focal position by beam control system 10, and meanwhile, the laser power of laser instrument 11 output also can be controlled by controller 1.
In the present invention: the function of working substance supply device 5 is transferring working medium, working medium is delivered to the appropriate location between the two poles of the earth, can supplement in time after working medium ablation is complete.Working medium can be delivered to precalculated position according to working medium ablation situation by working substance supply device 5 automatically.
Working medium 6 is carried by working substance supply device 5 and fixes, and partial ionized gas and particulate matter that laser ablation working medium produces fully enter among discharge channel.Working medium 6 is can at the solid of longer-term storage under space environment, as long as material can also partial ionization all can as the working medium of thruster by laser ablation gasification, the working medium of thruster is generally Teflon or modified Teflon etc..Working medium can be metal or other conductive solids.
Plume preventer 9, between beam control system 10 and cathode-anode plate, is stoped the optical mirror plane polluting beam control system 10 from the granule of laser optical path effusion, gas and ion etc., harm is reduced to minimum degree by modes such as lens block.Plume preventer 9 is longer with the distance of working medium 6 end face, to ensure that plume preventer 9 is away from thruster plume center.
The control of the controlled device 1 of beam control system 10, the parameter such as scalable output beam quality, spot size and focal position, thus controlling the laser ablation process to working medium surface.
The control of the controlled device 1 of laser instrument 11, can be adjusted laser power etc..The laser that laser instrument 11 sends is directive working medium after beam control system 10 and plume preventer 9, and laser ablation working medium produces neutral gas, ion and the particulate matter differed in size.For coaxial type thruster, laser can from the oblique fire of anode nozzle afterbody to working medium, it is possible to opens aperture on anode, allows laser pass through directive working medium.For parallel plate electrode type thruster, laser may pass through the aperture directive working medium on pole plate, it is possible to from the side directive working medium of flat board pole plate.Laser beam is vertical with ion injection direction or becomes an oblique angle, and to allow, the minute surface of beam control system 10 is as far as possible few is subject to washing away of injection plume particle.
It is that coaxial type thruster working medium is as negative electrode schematic diagram with reference to Fig. 2, Fig. 2；Coaxial type anode 8 is the cylinder cartridge type of boring, described working medium 6 is metal or the good solid of its conductive capability, working medium 6 can simultaneously as coaxial type negative electrode 7, working medium 6 is solid cylinder structure, the inside of coaxial type anode 8 is fixed and stretched into working medium by working substance supply device, and working medium 6 is arranged on coaxial type anode 8 inside and is coaxially disposed with coaxial type anode 8.Discharge channel is defined between working medium 6 (i.e. coaxial type negative electrode 7) and coaxial type anode 8.Working medium 6 simultaneously as the negative electrode of thruster, can be supplemented after working medium ablation is complete in time, so can eliminate the problem that cathode burning corrosion is serious.
Described laser beam exports from the discharge channel that coaxial type negative electrode 7, coaxial type anode 8 are formed when injecting, for ensureing that plume preventer 9 affects from plume as far as possible, laser is angled with the central shaft of coaxial type anode 8, this angle is the bigger the better when ensureing the smooth ablation working medium of laser, and to deviate the central shaft of coaxial type anode 8 in allowed band more remote more good for plume preventer 9 simultaneously.
It is laser beam traverse coaxial type anode aperture directive working medium schematic diagram with reference to Fig. 3, Fig. 3；When adopting coaxial type negative electrode 7, coaxial type anode 8 to form discharge channel, laser beam may pass through the aperture directive working medium opened on coaxial type anode 8.
What Fig. 1, Fig. 2, Fig. 3 provided is adopt coaxial type negative electrode, coaxial type anode as discharge channel, during the work of this coaxial type thruster, laser ablation working medium generating section ionized gas and particulate matter, negative and positive the two poles of the earth form stabling current under ablation resultant is supported, electric current forms self induction magnetic field, plasma accelerate vertically in electric field and self induction magnetic field after to outer ejection.When self-induction magnetic field is inadequate, can installing field coil 3 outside thruster anode additional, produce along the axial complementary field of thruster, plasma forms peripheral force in complementary field, by expanding nozzle, rotation function is converted into axial energy, promotes thruster propulsive performance.
Fig. 4 is laser beam from parallel plate electrode side directive working medium schematic diagram；The present invention also can adopt planar cathode 13, flat board anode 12 as discharge channel.Planar cathode 13, flat board anode 12 are slab construction, and planar cathode 13 is parallel with flat board anode 12 or arranges in certain subtended angle, forms discharge channel between planar cathode 13 and flat board anode 12.Working medium stretches in the discharge channel between planar cathode 13 and flat board anode 12 from the side of discharge channel, is provided with division board between working medium 6 and planar cathode 13 and flat board anode 12.Laser beam tilts through discharge channel directive working medium 6 from the opposite side of discharge channel.
Fig. 5 is laser through the aperture directive working medium schematic diagram on parallel plate electrode, and same employing planar cathode 13, flat board anode 12 are as discharge channel.Planar cathode 13, flat board anode 12 are slab construction, and planar cathode 13 is parallel with flat board anode 12 or arranges in certain subtended angle, forms discharge channel between planar cathode 13 and flat board anode 12.Working medium stretches in the discharge channel between planar cathode 13 and flat board anode 12 from the side of discharge channel, is provided with division board between working medium 6 and planar cathode 13 and flat board anode 12.Offering the through hole of confession laser beam traverse in planar cathode 13, laser beam passes in the working medium 6 in directive discharge channel from this through hole.
Fig. 4 and Fig. 5 adopts planar cathode, flat board anode to build discharge channel, when thruster adopts parallel plate cathode 13, parallel plate anodes 12, working medium is placed between two-plate, laser ablation working medium generating section ionized gas and particulate matter, negative and positive the two poles of the earth form stabling current under ablation resultant is supported, electric current forms the induced field being perpendicular to the sense of current simultaneously, and cation is accelerated ejection by electromagnetic force in electromagnetic field, thus producing thrust.Can arrange in this parallel plate electrode type thruster discharge channel both sides and produce permanent magnet or solenoid with discharge current self induction magnetic field complementary field in the same direction to promote thruster propulsive performance.
Field coil power supply 2 and field coil 3 are used for producing externally-applied magnetic field, and parallel plate electrode type thruster sectional adds being perpendicular to discharge channel axis and being parallel to the magnetic field of pole plate；Coaxial type thruster is added the magnetic field being parallel to discharge channel axis.Binding plasma accelerating performance, changes each section of magnetic field size of discharge channel axis respectively, to improve thruster discharge waveform raising thruster performance.
In sum; although the present invention is disclosed above with preferred embodiment; so it is not limited to the present invention; any those of ordinary skill in the art; without departing from the spirit and scope of the present invention; when doing various change and retouching, therefore protection scope of the present invention ought be as the criterion depending on the scope that claims define.
Claims (14)
1. the magnetic plasma propeller that a laser is supported, including the thruster power supply powered to electrical equipment each in thruster, thruster power supply is supplied to thruster after converted for satellite platform electric energy, it is characterized in that: also include working substance supply device, working medium, negative electrode, anode and laser generating mechanism, discharge channel is defined between negative electrode and anode, it is arranged on outside discharge channel for fixing and transferring working medium working substance supply device, described working medium is solid working medium, working medium stretches in discharge channel, laser instrument generating mechanism launches laser beam ablation working medium in discharge channel, laser beam continuous ablation working medium generating section ionized gas and particulate matter enter among discharge channel.
2. the magnetic plasma propeller that laser according to claim 1 is supported, it is characterized in that: thruster also includes controller, described controller is connected with thruster power supply and laser generating mechanism, the electric current of monitoring control devices thruster power supply output and voltage, controller controls the laser power of laser generating mechanism output, regulates its output beam quality, spot size and focal position.
3. the magnetic plasma propeller that laser according to claim 2 is supported, it is characterized in that: described laser generating mechanism includes beam control system and laser instrument, described beam control system and laser instrument are all connected with controller, the laser power of laser instrument output is by controller control, and the laser beam of laser instrument output is regulated output beam quality, spot size and focal position by beam control system.
4. the magnetic plasma propeller that laser according to claim 3 is supported, it is characterized in that: described laser generating mechanism also includes plume preventer, described plume protection dress is being positioned on the laser optical path between beam control system and discharge channel, for preventing the optical mirror plane of plume contamination beam control system.
5. the magnetic plasma propeller that the laser according to any one claim in Claims 1-4 is supported, it is characterized in that: described anode is nozzle type or the cylinder cartridge type of the shrinkage expansion of boring, and described negative electrode is arranged on anode interior and negative electrode and anode is coaxially disposed.
6. the magnetic plasma propeller that laser according to claim 5 is supported, it is characterised in that: described working medium is simultaneously as negative electrode.
7. the magnetic plasma propeller that laser according to claim 5 is supported, it is characterized in that: described laser beam exports directive working medium from discharge channel, the central axis of laser beam and coaxial type anode forms an angle, the angle of angle ensure laser beam can ablation working medium when big as far as possible, plume preventer deviates the rotating shaft of coaxial type anode as far as possible in thruster physical dimension allowed band simultaneously.
8. the magnetic plasma propeller that laser according to claim 5 is supported, it is characterised in that: described anode offers the through hole for laser beam traverse, the through hole directive working medium that described laser beam is offered on anode.
9. the magnetic plasma propeller that laser according to claim 5 is supported, it is characterized in that: outside described anode, install field coil additional, field coil is powered by field coil power supply, and field coil produces approximately along the axial complementary field of thruster to improve thruster performance.
10. the magnetic plasma propeller that laser according to claim 9 is supported, it is characterised in that: controller can control field coil power supply, regulates the size of current of field coil, thus strengthening or reducing externally-applied magnetic field.
11. the magnetic plasma propeller that the laser according to any one claim in Claims 1-4 is supported, it is characterised in that: described negative electrode and anode are slab construction, and described negative electrode is parallel with anode or arranges in certain subtended angle.
12. the magnetic plasma propeller that laser according to claim 11 is supported, it is characterised in that: laser beam is from the side directive working medium of discharge channel；Or described yin, yang pole plate offers the through hole for laser beam traverse, the through hole directive working medium that described laser beam is offered on yin, yang pole plate.
13. the magnetic plasma propeller that laser according to claim 11 is supported, it is characterised in that: permanent magnet or solenoid are arranged in discharge channel both sides, produce with self induction magnetic field complementary field in the same direction to promote thruster propulsive performance.
14. the magnetic plasma propeller that laser according to claim 1 is supported, it is characterised in that laser instrument can continuous mode work or Burst-mode operation.
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